There is provided a method to account for aircraft angle of attack effects in engine noise shielding in aircraft configurations having one or more engines mounted above a wing or a lifting body. The method includes computing a local flow field from a known standard full aircraft configuration oriented at a nonzero angle of attack. The method further includes computing a mean flow field in a test dataset from a small scale aircraft model test configuration oriented at a zero angle of attack. The method further includes matching the local flow field with the mean flow field to identify a selected noise measurement dataset. The method further includes rotating the selected noise measurement dataset in a far field directivity rotation angle to match the nonzero angle of attack, thus resulting in engine noise shielding results for the full aircraft configuration at the nonzero angle of attack.
Legal claims defining the scope of protection. Each claim is shown in both the original legal language and a plain English translation.
1. A method to account for aircraft angle of attack effects in engine noise shielding tests in aircraft configurations having one or more engines mounted above a wing or a lifting body, the method implemented using a computer software program product stored on a computer readable storage medium on a computer, the method comprising: computing with a computer software program product stored on a computer readable storage medium on a computer a local flow field from a full aircraft configuration oriented at a nonzero angle of attack to obtain a computed overall local flow output computed from one or more local flow parameters comprising a Mach number distribution, a velocity vector field, a total pressure, and a total temperature, the full aircraft configuration comprising a hybrid wing body aircraft having one or more engines mounted above a wing or a lifting body of the hybrid wing body aircraft; computing with the computer software program product on the computer a mean flow field in a test dataset from an aircraft model test configuration oriented at a zero angle of attack to obtain one or more test conditions comprising a Mach number distribution, a velocity vector field, a total pressure, and a total temperature, the aircraft model test configuration comprising one or more engines mounted over a flat plate; comparing with the computer software program product on the computer the local flow field with the mean flow field to identify a selected noise measurement dataset; and, rotating with the computer software program product on the computer the selected noise measurement dataset in a far field directivity rotation angle to match the nonzero angle of attack, thus resulting in engine noise shielding results for the full aircraft configuration at the nonzero angle of attack.
This invention relates to aircraft noise testing, specifically accounting for angle of attack effects in engine noise shielding evaluations for aircraft with engines mounted above wings or lifting bodies. The problem addressed is the need to accurately assess engine noise shielding in realistic flight conditions where the aircraft operates at non-zero angles of attack, while traditional testing often uses simplified models at zero angle of attack. The method involves using a computer software program to simulate and compare flow fields. First, it computes a local flow field for a full aircraft configuration (e.g., a hybrid wing body aircraft) at a non-zero angle of attack, generating outputs like Mach number distribution, velocity vector field, total pressure, and total temperature. Second, it computes a mean flow field from a test configuration (e.g., engines mounted over a flat plate) at zero angle of attack, producing similar flow parameters. The software then compares these flow fields to select a relevant noise measurement dataset. Finally, it rotates this dataset in the far field to align with the non-zero angle of attack, yielding accurate engine noise shielding results for the full aircraft configuration. This approach improves the accuracy of noise predictions by accounting for real-world flight conditions.
2. The method of claim 1 wherein computing the local flow field further comprises computing a computed overall mean flow for the full aircraft configuration and using the computed overall mean flow and the one or more local flow parameters of the full aircraft configuration to generate the local flow field.
This invention relates to computational fluid dynamics (CFD) for aircraft design, specifically improving the accuracy of local flow field calculations. The problem addressed is the challenge of accurately modeling airflow around complex aircraft configurations, where interactions between different components (e.g., wings, fuselage, control surfaces) significantly affect local flow characteristics. Traditional methods often fail to capture these interactions, leading to inaccuracies in performance predictions. The invention provides a method to compute a local flow field for an aircraft by first determining an overall mean flow for the entire aircraft configuration. This mean flow is then combined with one or more local flow parameters specific to the aircraft's components to generate a more accurate local flow field. The local flow parameters may include factors like pressure gradients, velocity distributions, or turbulence effects near specific surfaces. By integrating the overall mean flow with these localized parameters, the method improves the fidelity of CFD simulations, particularly in regions where component interactions are critical, such as wing-fuselage junctions or control surface interactions. This approach enhances the reliability of aerodynamic performance predictions, aiding in aircraft design and optimization. The method is applicable to various aircraft configurations, including fixed-wing and rotary-wing designs, and can be implemented in existing CFD software.
3. The method of claim 1 wherein the local flow field is in front of one or more engines of the full aircraft configuration, and wherein the mean flow field is in front of one or more engines of the aircraft model test configuration.
This invention relates to aerodynamic testing and simulation, specifically for aircraft configurations involving engine placement. The problem addressed is accurately modeling the flow field interactions between an aircraft and its engines during testing, particularly when comparing full aircraft configurations to scaled-down model test configurations. The invention provides a method to ensure consistency in flow field analysis by aligning the local flow field in front of the engines of the full aircraft with the mean flow field in front of the engines of the model test configuration. This alignment helps maintain realistic aerodynamic conditions during testing, improving the accuracy of performance predictions. The method involves adjusting the model test configuration to replicate the flow characteristics observed in the full aircraft, accounting for differences in scale and operational conditions. By ensuring the mean flow field in the test setup matches the local flow field in the full configuration, the method reduces discrepancies in aerodynamic data, leading to more reliable design and validation processes. The approach is particularly useful in wind tunnel testing and computational fluid dynamics (CFD) simulations where engine-induced flow effects must be accurately represented.
4. The method of claim 1 wherein comparing the local flow field to the mean field further comprises if there is a match between the local flow field and the mean flow field, the mean flow field is the selected noise measurement dataset, and if there is not a match between the local flow field and the mean flow field, dataset interpolation is performed to obtain the selected noise measurement dataset.
This invention relates to noise measurement and analysis in fluid flow systems, particularly for identifying and selecting appropriate noise measurement datasets based on flow field comparisons. The problem addressed is the challenge of accurately characterizing noise in fluid systems where flow conditions vary, requiring adaptive selection of noise measurement datasets to ensure reliable analysis. The method involves comparing a local flow field, representing the current fluid flow conditions, to a mean flow field, which is a reference dataset. If the local flow field matches the mean flow field, the mean flow field is directly used as the selected noise measurement dataset. If there is no match, dataset interpolation is performed to generate an interpolated dataset that aligns with the local flow field, which then becomes the selected noise measurement dataset. This interpolation ensures that the noise measurements remain accurate even when the local flow conditions deviate from the mean reference. The interpolation process may involve blending multiple noise measurement datasets or adjusting parameters to match the local flow field characteristics. This adaptive approach improves the accuracy of noise analysis in dynamic fluid systems by dynamically selecting or generating the most relevant noise measurement dataset based on real-time flow conditions. The method is particularly useful in applications where fluid flow variability affects noise measurements, such as in aerospace, automotive, or industrial fluid systems.
5. The method of claim 1 wherein the full aircraft configuration comprises at least an airframe model and a wind tunnel assembly, or comprises full scale aircraft flight conditions.
This invention relates to aircraft design and testing, specifically methods for simulating and analyzing aircraft configurations. The problem addressed is the need for accurate and comprehensive testing of aircraft designs under realistic conditions, whether through physical models or full-scale flight simulations. The method involves creating a full aircraft configuration that includes at least an airframe model and a wind tunnel assembly, or simulates full-scale aircraft flight conditions. The airframe model represents the structural components of the aircraft, while the wind tunnel assembly allows for aerodynamic testing in controlled environments. Alternatively, the method can simulate full-scale flight conditions, providing data on how the aircraft would perform in actual flight. This approach ensures that both physical and computational testing are integrated to validate aircraft performance, aerodynamics, and structural integrity. The method may also include adjusting parameters such as airflow, pressure, or flight dynamics to refine the design. By combining physical and simulated testing, the invention improves the accuracy and reliability of aircraft development processes.
6. The method of claim 1 wherein the aircraft model test configuration comprises one or more engine simulators mounted over the flat plate oriented at a zero angle of attack.
This invention relates to aircraft model testing, specifically addressing the need for accurate aerodynamic and propulsion system evaluations in wind tunnel environments. The method involves configuring an aircraft model with one or more engine simulators mounted over a flat plate positioned at a zero angle of attack. The flat plate provides a stable mounting surface for the engine simulators, which simulate the thrust and airflow characteristics of actual aircraft engines. By orienting the flat plate at zero angle of attack, the setup ensures consistent and repeatable test conditions, minimizing aerodynamic interference from the mounting structure. The engine simulators replicate the performance of real engines, allowing for precise measurement of their interaction with the aircraft model's aerodynamics. This configuration enables researchers to study the effects of engine thrust, exhaust flow, and other propulsion-related factors on the aircraft's overall performance without the complexities introduced by angled mounting or unstable test setups. The method is particularly useful for validating computational models and refining aircraft designs before full-scale testing or production.
7. The method of claim 1 wherein the one or more engines mounted above the wing or the lifting body are substantially shielded by a top of the wing or a top of the lifting body.
This invention relates to aircraft propulsion systems, specifically addressing the challenge of improving aerodynamic efficiency and reducing drag by strategically positioning and shielding propulsion engines. The system involves mounting one or more engines above a wing or lifting body structure, where the engines are substantially shielded by the top surface of the wing or lifting body. This configuration minimizes aerodynamic interference between the engines and the airflow over the wing, reducing drag and improving overall aircraft performance. The shielding effect helps maintain smooth airflow, reducing turbulence and improving lift-to-drag ratios. The engines may be mounted in a recessed or integrated manner to further enhance aerodynamic efficiency. This approach is particularly useful for high-speed or fuel-efficient aircraft designs, where minimizing drag and optimizing propulsion placement are critical. The invention ensures that the engines do not disrupt the wing's airflow while still providing effective thrust, leading to better fuel economy and performance. The system may also incorporate additional features such as variable engine positioning or adaptive shielding to further optimize performance under different flight conditions.
8. The method of claim 1 wherein the method reduces costs and saves time by avoiding conducting large scale wind tunnel tests and full scale aircraft flight tests by using test datasets from the aircraft model test configuration to account for the nonzero angle of attack effects.
This invention relates to aircraft design and testing, specifically reducing costs and time by minimizing the need for large-scale wind tunnel tests and full-scale flight tests. Traditional aircraft development relies heavily on these expensive and time-consuming tests to evaluate aerodynamic performance, particularly at nonzero angles of attack. The invention addresses this by leveraging test datasets from a scaled aircraft model to simulate and account for the effects of nonzero angles of attack. By using these datasets, the method avoids the need for extensive physical testing, thereby reducing costs and accelerating the design process. The approach involves analyzing the model test data to derive aerodynamic characteristics that would otherwise require full-scale testing. This allows engineers to validate and refine aircraft designs more efficiently, ensuring performance accuracy without the high expenses and delays associated with traditional testing methods. The technique is particularly useful in early-stage design phases where iterative testing is critical but resource constraints are significant. By focusing on model-based simulations, the invention streamlines the development workflow while maintaining reliability in aerodynamic assessments.
9. A method for determining operational engine output noise levels as related to angles of attack in aircraft configurations for which one or more engines are mounted above a wing or a lifting body and substantially shielded by the wing or the lifting body, the method comprising: computing with a computer software program product on a computer a computed overall mean flow from a full aircraft configuration oriented at a nonzero angle of attack, the full aircraft configuration comprising a hybrid wing body aircraft having one or more engines mounted above a wing or a lifting body of the hybrid wing body aircraft; computing with the computer software program product on the computer a local flow field using the computed overall mean flow and a plurality of local flow parameters from the full aircraft configuration, the plurality of local flow parameters comprising a Mach number distribution, a velocity vector field, a total pressure, and a total temperature; computing with the computer software program product on the computer a mean flow field in a test dataset from an aircraft model test configuration oriented at a zero angle of attack to obtain one or more test conditions comprising a Mach number distribution, a velocity vector field, a total pressure, and a total temperature, the aircraft model test configuration comprising one or more engines mounted over a flat plate; comparing with the computer software program product on the computer the local flow field to the mean flow field, wherein if there is a match between the local flow field and the mean flow field, the mean flow field is selected as a dataset identification, and wherein if there is no match between the local flow field and the mean flow field, dataset interpolation is performed to select the dataset identification; and, rotating with the computer software program product on the computer the selected dataset identification in a far field directivity rotation angle to match the nonzero angle of attack, thus resulting in engine output noise level results for the full aircraft configuration at the nonzero angle of attack.
This invention relates to a method for predicting engine noise levels in aircraft configurations where engines are mounted above a wing or lifting body and shielded by it. The problem addressed is accurately determining noise output at various angles of attack, which is challenging due to aerodynamic interactions between the engines, wing, and airflow. The method uses computational fluid dynamics to analyze airflow characteristics. First, a full aircraft model at a nonzero angle of attack is simulated to compute overall mean airflow, including Mach number distribution, velocity vectors, total pressure, and total temperature. Next, local flow fields around the engines are calculated using these parameters. Separately, a simplified aircraft model (engines over a flat plate) is tested at zero angle of attack to generate a baseline mean flow dataset. The local flow field from the full aircraft is compared to this dataset. If a match is found, that dataset is selected; if not, interpolation is used to create a matching dataset. Finally, the selected dataset is rotated to account for the original nonzero angle of attack, producing noise level predictions for the full aircraft configuration. This approach improves noise modeling by accounting for complex aerodynamic shielding effects at different flight attitudes.
10. The method of claim 9 wherein the local flow field is in front of one or more engines of the full aircraft configuration, and wherein the mean flow field is in front of one or more engines of the aircraft model test configuration.
This invention relates to aerodynamic testing and simulation, specifically for aircraft configurations involving engine placement. The problem addressed is accurately modeling the aerodynamic effects of engines on an aircraft's flow field during testing, particularly when comparing full aircraft configurations to scaled-down test models. The method involves analyzing flow fields in two distinct configurations: a full aircraft setup and a scaled test model. In the full aircraft configuration, the local flow field is measured or simulated in front of one or more engines. Similarly, in the scaled test model configuration, the mean flow field is measured or simulated in the same relative position in front of the engines. By comparing these flow fields, engineers can assess how engine placement and operation influence aerodynamic performance, such as drag, lift, and stability, across different aircraft scales. The technique ensures that test results from scaled models accurately reflect real-world conditions, improving the reliability of aerodynamic predictions. This is particularly useful in early-stage aircraft design, where computational and wind tunnel testing must account for engine-induced flow disturbances. The method may involve computational fluid dynamics (CFD) simulations, wind tunnel experiments, or a combination of both to capture the necessary flow field data. The comparison of local and mean flow fields helps identify discrepancies between test models and full-scale aircraft, allowing for adjustments in design or testing parameters.
11. The method of claim 9 wherein the full aircraft configuration comprises at least an airframe model and a wind tunnel assembly, or comprises full scale aircraft flight conditions.
This invention relates to aircraft testing and simulation, specifically addressing the need for accurate and comprehensive aerodynamic analysis. The method involves creating a full aircraft configuration that includes an airframe model and a wind tunnel assembly, or it can simulate full-scale aircraft flight conditions. The airframe model represents the physical structure of the aircraft, while the wind tunnel assembly allows for controlled aerodynamic testing in a laboratory environment. Alternatively, the method can replicate real-world flight conditions to assess performance, stability, and efficiency. The approach ensures that aerodynamic properties are evaluated under realistic scenarios, whether in a controlled wind tunnel or through computational simulations. This enables engineers to optimize aircraft design, reduce drag, and improve overall flight performance. The method supports both small-scale testing and full-scale flight condition simulations, providing flexibility in the testing process. By integrating these elements, the invention enhances the accuracy and reliability of aerodynamic assessments, leading to safer and more efficient aircraft designs.
12. The method of claim 9 wherein the aircraft model test configuration comprises one or more engine simulators mounted over a flat plate oriented at a zero angle of attack.
This invention relates to aircraft model testing, specifically addressing the need for accurate aerodynamic and propulsion system evaluations in controlled environments. The method involves testing an aircraft model in a configuration that includes one or more engine simulators mounted over a flat plate. The flat plate is oriented at a zero angle of attack, meaning it is positioned horizontally to simulate level flight conditions. This setup allows for precise measurement of airflow interactions between the aircraft model and the engine simulators without the complications introduced by angled surfaces. The engine simulators replicate the thrust and airflow characteristics of actual aircraft engines, enabling realistic testing of propulsion system performance and aerodynamic effects. The flat plate provides a stable, uniform surface to support the model and simulators, ensuring consistent test conditions. This configuration is particularly useful for evaluating the impact of engine placement, thrust vectoring, and other propulsion-related factors on aircraft stability and efficiency. The method supports detailed aerodynamic analysis by isolating variables such as angle of attack, allowing researchers to focus on specific interactions between the aircraft model and its propulsion system. The setup is adaptable for various aircraft designs and engine types, making it a versatile tool for aeronautical research and development.
13. The method of claim 9 wherein the method reduces costs and saves time by avoiding conducting large scale wind tunnel tests and full scale aircraft flight tests by using test datasets from the aircraft model test configuration to account for the nonzero angle of attack effects.
This invention relates to aircraft design and testing, specifically reducing costs and time by minimizing the need for large-scale wind tunnel tests and full-scale flight tests. The method leverages test datasets from an aircraft model test configuration to account for nonzero angle of attack effects during flight. Traditional aircraft testing involves extensive wind tunnel and flight tests to validate aerodynamic performance, which are expensive and time-consuming. The invention addresses this by using pre-existing test data from model configurations to simulate and predict aerodynamic behavior at various angles of attack, eliminating the need for additional large-scale testing. The method involves analyzing the test datasets to derive aerodynamic characteristics, such as lift, drag, and stability, under different flight conditions. By incorporating these datasets into computational models, engineers can accurately predict aircraft performance without conducting full-scale tests. This approach reduces development costs, accelerates the design process, and improves efficiency in aircraft testing and validation. The technique is particularly useful for optimizing wing and control surface designs, ensuring compliance with performance requirements while minimizing physical testing. The invention streamlines the testing phase, making aircraft development more cost-effective and time-efficient.
14. A system to account for aircraft angle of attack effects in engine noise shielding tests in aircraft configurations having one or more engines mounted above a wing or a lifting body, the system implemented with a computer software program product stored on a computer readable storage medium on a computer, the system comprising: a flow computation element that generates a computed overall mean flow from a full aircraft configuration oriented at a nonzero angle of attack, the full aircraft configuration comprising a hybrid wing body aircraft having one or more engines mounted above a wing or a lifting body of the hybrid wing body aircraft; a local flow extraction element that generates a local flow field from the full aircraft configuration, the local flow field using the computed overall mean flow and a plurality of local flow parameters from the full aircraft configuration, the plurality of local flow parameters comprising a Mach number distribution, a velocity vector field, a total pressure, and a total temperature; a data extraction element that generates a mean flow field from an aircraft model test configuration oriented at a zero angle of attack, the mean flow field being generated from a test dataset from the aircraft model test configuration to obtain one or more test conditions comprising a Mach number distribution, a velocity vector field, a total pressure, and a total temperature, the aircraft model test configuration comprising one or more engines mounted over a flat plate; a local flow matching element that generates a plurality of local flow matching conclusions; a dataset identification element comprising a noise measurement dataset from the aircraft model test configuration; a directivity rotation element that generates a noise measurement dataset for the full aircraft configuration; and, a results dataset comprising engine noise shielding for the full aircraft configuration at the nonzero angle of attack.
This system addresses the challenge of accurately accounting for aircraft angle of attack effects in engine noise shielding tests, particularly for hybrid wing body aircraft with engines mounted above the wing or lifting body. The system uses computational and experimental data to simulate and analyze noise shielding under realistic flight conditions. It begins by generating a computed overall mean flow from a full aircraft configuration at a nonzero angle of attack, capturing aerodynamic interactions between the aircraft and its engines. A local flow extraction element then derives a detailed local flow field, including Mach number distribution, velocity vector field, total pressure, and total temperature, from the full aircraft configuration. Separately, a mean flow field is generated from an aircraft model test configuration at zero angle of attack, using test data from a simplified setup with engines mounted over a flat plate. The system matches local flow conditions between the full aircraft and test configurations to ensure comparable conditions. A dataset identification element selects noise measurement data from the test configuration, which is then rotated to align with the full aircraft's orientation, producing a noise measurement dataset for the full configuration. The final results dataset provides engine noise shielding data for the full aircraft at the nonzero angle of attack, enabling accurate noise performance assessment under realistic flight conditions.
15. The system of claim 14 wherein the flow computation element has a flow computation input comprising known standard aircraft geometry and aircraft operation conditions from the full aircraft configuration, and has a flow computation output comprising the computed overall mean flow.
This invention relates to aerodynamics and aircraft design, specifically addressing the challenge of accurately computing airflow characteristics for aircraft configurations. The system calculates the overall mean flow around an aircraft by leveraging known standard aircraft geometry and operational conditions. The flow computation element processes these inputs to generate a computed overall mean flow output, which can be used for aerodynamic analysis, performance optimization, or design validation. The system integrates with a full aircraft configuration, ensuring that the computed flow data is contextually relevant to the aircraft's operational environment. By standardizing input parameters and automating flow calculations, the invention improves efficiency and accuracy in aerodynamic assessments, reducing reliance on manual computations or empirical approximations. The computed mean flow can be applied to various aerodynamic studies, including drag estimation, lift distribution, and stability analysis, supporting more informed design decisions. The system's modular approach allows for adaptability across different aircraft types and operational scenarios, enhancing its utility in both research and industrial applications.
16. The system of claim 14 wherein the local flow extraction element has a local flow extraction input comprising the computed overall mean flow and a plurality of known standard local flow parameters from the full aircraft configuration, and has a local flow extraction output comprising the local flow field.
A system for aircraft aerodynamics analysis computes local flow fields from overall mean flow data. The system addresses the challenge of accurately modeling complex airflow interactions around aircraft by extracting detailed local flow characteristics from broader aerodynamic measurements. The system includes a local flow extraction element that processes input data comprising the computed overall mean flow and a set of known standard local flow parameters specific to the full aircraft configuration. These inputs are used to generate a local flow field output, which provides detailed airflow information at specific regions of the aircraft. The system leverages pre-determined local flow parameters to refine the overall mean flow data, enabling precise aerodynamic simulations and performance predictions. This approach enhances computational efficiency by avoiding full-scale simulations while maintaining accuracy in critical flow regions. The system is particularly useful for optimizing aircraft design, improving fuel efficiency, and reducing drag through targeted aerodynamic adjustments. By integrating standard local flow parameters with mean flow data, the system ensures reliable and scalable aerodynamic modeling for various aircraft configurations.
17. The system of claim 14 wherein the data extraction element has a data extraction input comprising test conditions from the aircraft model test configuration, and has a data extraction output comprising a noise dataset and a flow dataset, the flow dataset comprising the mean flow field.
This invention relates to aircraft modeling and testing systems, specifically addressing the challenge of efficiently extracting and analyzing aerodynamic and acoustic data from aircraft model tests. The system includes a data extraction element that processes test conditions from an aircraft model test configuration to generate two key datasets: a noise dataset and a flow dataset. The flow dataset specifically includes the mean flow field, which represents the average airflow characteristics around the aircraft model during testing. This extracted data is used to evaluate the aerodynamic performance and noise characteristics of the aircraft model under various test conditions. The system enables engineers to assess how different configurations or modifications to the aircraft model affect its performance and noise output, facilitating optimization of design parameters. By automating the extraction and analysis of these datasets, the system reduces manual effort and improves the accuracy of aerodynamic and acoustic evaluations in aircraft development. The invention is particularly useful in wind tunnel testing and computational fluid dynamics (CFD) simulations, where precise data extraction is critical for validating aircraft designs.
18. The system of claim 14 wherein the local flow matching element has a local flow matching input comprising the local flow field and the mean flow field, and has a local flow matching output comprising the plurality of local flow matching conclusions.
This invention relates to a system for analyzing fluid flow dynamics, particularly in applications where local flow characteristics need to be compared or matched to a broader mean flow field. The problem addressed is the difficulty in accurately correlating localized flow variations with overall flow patterns, which is critical in fields such as aerodynamics, fluid mechanics, and environmental monitoring. The system includes a local flow matching element that processes both a local flow field and a mean flow field. The local flow field represents detailed flow measurements or simulations at a specific location, while the mean flow field provides a broader, averaged flow profile. The local flow matching element compares these inputs to generate a set of local flow matching conclusions. These conclusions may include statistical correlations, pattern matches, or deviations between the local and mean flow fields, helping users identify anomalies, optimize flow conditions, or validate simulation models. The system may also include additional components, such as sensors or computational modules, to gather or preprocess the flow data before analysis. The local flow matching element may employ algorithms like regression analysis, machine learning, or signal processing to derive meaningful insights from the flow data. The output conclusions can be used for real-time adjustments, predictive modeling, or quality control in industrial or scientific applications. This approach improves accuracy in flow analysis by integrating localized and global flow data, addressing limitations in traditional methods that rely solely on either local or mean flow measurements.
19. The system of claim 14 wherein the local flow matching element compares the local flow field with the mean flow field such that if there is a match between the local flow field and the mean flow field, the mean flow field is selected as the dataset identification element, and such that if there is not a match between the local flow field and the mean flow field, dataset interpolation is performed to obtain the dataset identification element.
This invention relates to a system for identifying and selecting datasets in fluid dynamics analysis, particularly for matching local flow fields to reference datasets. The system addresses the challenge of accurately identifying and interpolating flow field data to improve computational efficiency and accuracy in fluid dynamics simulations. The system includes a local flow matching element that compares a local flow field with a mean flow field. If the local flow field matches the mean flow field, the mean flow field is selected as the dataset identification element. If there is no match, dataset interpolation is performed to generate the dataset identification element. The interpolation process ensures that the selected dataset closely approximates the local flow field, even when an exact match is not available. The system also includes a dataset storage element that stores multiple flow field datasets, allowing for flexible selection and interpolation. The interpolation method may involve linear or non-linear techniques to blend datasets based on the local flow field characteristics. This approach enhances the accuracy of fluid dynamics simulations by dynamically adjusting the reference dataset to better represent the local flow conditions. By dynamically selecting or interpolating datasets, the system improves the efficiency and reliability of fluid dynamics modeling, reducing computational overhead while maintaining high accuracy. This is particularly useful in applications requiring real-time or high-fidelity simulations, such as aerodynamics, weather modeling, and industrial fluid flow analysis.
20. The system of claim 19 wherein the dataset interpolation is performed with a dataset interpolation element having a dataset interpolation input comprising a noise measurement dataset from the aircraft model test configuration and a definition for interpolated conditions, and having a dataset interpolation output comprising an interpolated noise measurement dataset.
The system relates to aircraft noise measurement and analysis, specifically addressing the challenge of accurately interpolating noise data from aircraft model tests to predict performance under different conditions. Aircraft testing generates noise measurement datasets under specific configurations, but real-world conditions vary, requiring interpolation to estimate noise levels for untested scenarios. The system includes a dataset interpolation element that processes a noise measurement dataset from an aircraft model test configuration along with a definition of interpolated conditions. The interpolation element generates an interpolated noise measurement dataset, allowing engineers to predict noise performance for conditions not directly measured during testing. This enables more comprehensive analysis and validation of aircraft designs without requiring additional physical tests. The interpolation process ensures that noise predictions are based on actual test data, improving accuracy and reliability compared to theoretical models alone. The system supports aerospace engineers in optimizing aircraft designs for noise reduction and compliance with regulatory standards.
21. The system of claim 14 wherein the directivity rotation element has a directivity rotation input comprising the noise measurement dataset and a nonzero angle of attack, and has a directivity rotation output comprising the noise measurement dataset for the full aircraft configuration.
This invention relates to aircraft noise measurement systems, specifically addressing the challenge of accurately capturing noise data from an aircraft in various flight configurations. The system includes a directivity rotation element that processes noise measurement data to account for different aircraft orientations. The directivity rotation element receives a noise measurement dataset and a nonzero angle of attack as inputs. It then generates a directivity rotation output, which provides the noise measurement dataset adjusted for the full aircraft configuration, including variations in orientation. This adjustment ensures that noise measurements are consistent and comparable across different flight conditions. The system may also include components for collecting raw noise data, processing it to remove background noise, and analyzing the results to determine noise characteristics. The directivity rotation element's ability to handle varying angles of attack allows for comprehensive noise assessment, which is critical for aircraft design, certification, and operational efficiency. The invention improves the accuracy and reliability of noise measurements by accounting for the dynamic nature of aircraft flight.
22. The system of claim 14 wherein the full aircraft configuration comprises at least an airframe model and a wind tunnel assembly, or comprises full scale aircraft flight conditions.
This invention relates to aircraft design and testing, specifically systems for simulating and analyzing aircraft configurations. The system addresses the challenge of accurately modeling aircraft performance under various conditions, including wind tunnel testing and full-scale flight scenarios. The system integrates a full aircraft configuration, which includes at least an airframe model and a wind tunnel assembly, or simulates full-scale aircraft flight conditions. The airframe model represents the physical structure of the aircraft, while the wind tunnel assembly allows for controlled aerodynamic testing. Alternatively, the system can replicate real-world flight conditions, enabling comprehensive performance analysis. The system may also incorporate additional components, such as propulsion systems or control surfaces, to enhance simulation accuracy. By providing a flexible framework for testing different configurations, the system supports efficient aircraft development and optimization. The invention aims to improve the reliability and efficiency of aircraft design processes by offering a versatile testing environment.
23. The system of claim 14 wherein the aircraft model test configuration comprises one or more engine simulators mounted over a flat plate oriented at a zero angle of attack.
The system relates to aircraft model testing, specifically for evaluating aerodynamic and propulsion interactions. The problem addressed is the need for accurate simulation of aircraft performance under controlled conditions, particularly focusing on engine effects on airflow and overall aircraft behavior. The system includes a test configuration featuring one or more engine simulators mounted over a flat plate. The flat plate is oriented at a zero angle of attack, meaning it is positioned horizontally to minimize aerodynamic interference and provide a stable reference plane. This setup allows for precise measurement of engine-induced airflow disturbances, thrust effects, and their impact on the aircraft model's stability and control. The engine simulators replicate real-world engine performance, including thrust output and exhaust flow characteristics, to simulate realistic flight conditions. The flat plate ensures consistent airflow conditions, reducing variability in test results. This configuration is particularly useful for validating computational models and refining aircraft design parameters before full-scale testing or production. The system enables engineers to assess how engine placement and operation influence aircraft behavior, optimizing performance and safety.
24. The system of claim 14 wherein the method reduces costs and saves time by avoiding conducting large scale wind tunnel tests and full scale aircraft flight tests by using test datasets from the aircraft model test configuration to account for the nonzero angle of attack effects.
This invention relates to aircraft design and testing, specifically reducing costs and time by minimizing the need for large-scale wind tunnel tests and full-scale flight tests. The system uses test datasets from an aircraft model test configuration to account for nonzero angle of attack effects, eliminating the necessity for extensive physical testing. The aircraft model test configuration includes a scaled-down representation of the aircraft, which is subjected to controlled testing conditions to generate data on aerodynamic performance. This data is then used to simulate and predict the behavior of the full-scale aircraft under various flight conditions, particularly those involving nonzero angles of attack. By leveraging this approach, the system avoids the high costs and time-consuming processes associated with traditional wind tunnel and flight testing. The method ensures accurate aerodynamic modeling by incorporating the effects of angle of attack, which are critical for assessing stability, control, and overall flight performance. The system integrates computational tools to analyze the test datasets, allowing engineers to refine aircraft designs iteratively without relying on physical prototypes. This reduces development time and costs while maintaining high accuracy in performance predictions. The invention is particularly useful in early-stage aircraft design, where rapid iteration and cost efficiency are essential.
Cooperative Patent Classification codes for this invention. Click any code to explore related patents in that topic.
October 29, 2010
September 10, 2013
Browse 5M+ US patents with plain-English claim translations and AI-generated analysis.